O2/H2 Advanced Maneuvering Propulsion Technology Program Engine System Studies. Volume III. 10,000-Pound-Thrust Bell Engine Configuration Design and Analysis.

Abstract

This report describes the analysis and design of an advanced high performing, reusable 10,000-pound-thrust rocket engine suitable for advanced maneuvering space missions. The engine, using O2/H2 propellants, is a staged-combustion bell nozzle configuration with a chamber pressure of 1800 psia and expansion area ratio of 400:1, and delivers a specific impulse of 471.8 lbf-sec/lbm. Included in the report are the configuration optimization, performance analysis, engine operation, maintenance, component design, development program and costs, and analysis of engine design variations. (Author)

Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1972
Accession Number
AD0892484

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Bell Nozzles
  • Combustion
  • Engines
  • Maintenance
  • Missions
  • Nozzles
  • Optimization
  • Propellants
  • Rocket Engines
  • Rockets
  • Space Missions
  • Specific Impulse
  • Thrust

Fields of Study

  • Physics

Readers

  • Aerospace Engineering.
  • Computer Science.
  • Rocket Propulsion.

Technology Areas

  • Space
  • Space - Hall-Effect Thruster